Ordnance ejector system for an aircraft

ABSTRACT

A ordnance ejector apparatus (10) for ejecting an ordnance from an aircraft includes a mechanical linkage comprising a forward bell crank (36) and a forward connecting link (46) and a rearward bell crank (50) and a rearward connecting link (60). A rail (24) releasably retains an ordnance (16) thereto and is pivotally connected at opposite ends (26, 28) to the forward connecting link (46) and the rearward connecting link (60). Two pyrotechnically operated pistons (78, 88) are disposed in end-to-end relation and act independently on the forward bell crank (36) and rearward bell crank (50). The rail (24) includes a plurality of ordnance retaining hooks (152) which are automatically actuated to release the ordnance (16) when the rail (24) is extended by the mechanical linkage. A mechanical hoist (108) is manually operated by a screw shaft (110) for manually extending the rail (24) to attach an ordnance (16) thereto.

TECHNICAL FIELD

The subject invention relates generally to bomb, flare and signaldropping, and more specifically to bomb, or ordnance, ejected from theexterior of an aircraft.

BACKGROUND ART

According to the well known principles of fluid dynamics, as an aircraftflies through the air, a boundary layer of turbulent air develops aboutall exterior surfaces of the aircraft. In order to properly deploy anordnance from underneath the aircraft, the ordnance must be pushedthrough this boundary layer before being fully released from control. Ifthe ordnance is not pushed through the boundary layer, the turbulent airwithin the boundary layer may act unpredictably upon the ordnance,perhaps causing it to bounce against the under surface of the aircraftthereby causing damage.

Typically, ordnance ejector systems function either by mechanicallinkages which push the ordnance through the turbulent boundary layer,or axially moving reciprocating shafts which push the ordnance throughthe turbulent boundary layer. Examples of the linkage type ordnanceejector systems include U.S. Pat. Nos. 4,440,365 to Holtrop, issued Apr.3, 1984, 4,679,751 to Peterson, issued July 14, 1987 and 4,600,171 toKalisz, issued July 15, 1986. An example of the axially movingreciprocating shaft type ordnance ejector system is the U.S. Pat. No.4,572,053 to Sosnowski et al., issued Feb. 25, 1986.

Typically, the linkage type ordnance ejector systems include a forwardand rearward linkage connected to a rail member, wherein the rail memberreleasably retains the ordnance thereto. It has been found particularlyadvantageous to individually control the forward and rearward linkagewith separate, dedicated actuators. Such actuators typically comprisepyrotechnically operated pistons. Individual control of the forward andrearward linkages allows the ordnance ejector system to be more easilyadapted to different ordnance types. That is, different types ofordnance may require different ejection velocities, different attitudesat release, etc. Unless independent control of the forward and rearwardlinkages is provided, such adaptations can not be made except byphysical changes to the individual links.

One significant concern which becomes particularly acute when theforward and rearward linkages are controlled by independent actuators isthe reaction forces placed upon the support frame structure when the twoindependent actuators are operated. According to the prior art, thesupport frame is designed from very strong and heavy members in order towithstand the reaction forces. However, the increased weight of thesupport frame has an adverse affect on the aircraft, as weight is alwaysa critical factor in air travel.

Because of this, many prior art devices have foregone independentcontrol of the forward and rearward linkages by separate actuators,favor of a single actuator so that the support frame does not need to befabricated from heavy structural members.

SUMMARY OF THE INVENTION AND ADVANTAGES

An ordnance ejector apparatus is provided for ejecting an ordnance froman aircraft. The apparatus comprises a support frame extending between aforward end and a rearward end for fixed attachment to an aircraft, arail extending between a forward end and a rearward end for releasablyretaining an ordnance thereto, a forward link means pivotally connectedbetween the forward end of the support frame and the forward end of therail for displacing the forward end of the rail a predetermined distancefrom the support frame, a rearward link means pivotally connectedbetween the rearward end of the support frame and the rearward end ofthe rail for displacing the rearward end of the rail a predetermineddistance from the support frame, a forward actuator means having anoutput stroke along a linear path for independently controlling thepivotal movement of the forward link means, and a rearward actuatormeans having an output stroke along a linear path for independentlycontrolling the pivotal movement of the rearward link means. Theinvention is characterized by the forward actuator means and therearward actuator means being fixedly aligned in an axially oppositelyextending disposition such that the linear output stroke of the forwardactuator means acts along a colinear and opposite direction from thelinear output stroke of the rearward actuator means to reduce thereaction forces between the forward and rearward actuator means.

The subject invention overcomes the deficiencies in the prior art byaligning the forward and rearward actuator means in an end-to-endorientation so that most, if not all, of the reaction forces occurringas a result of the actuators moving the respective forward and rearwardlink means are cancelled. Therefore, the support frame can be made lessrigid in the area supporting the actuators, that even the prior artsupport frames which only supported one single actuator. In other words,by balancing the reaction forces of the actuators, as does the subjectinvention, the entire ordnance ejector apparatus can be lighter inweight that the prior art apparatuses, and hence more desirable.

BRIEF DESCRIPTION OF THE DRAWINGS

Other advantages of the present invention will be readily appreciated asthe same becomes better understood by reference to the followingdetailed description when considered in connection with the accompanyingdrawings wherein:

FIG. 1 is an environmental view showing the subject invention disposedunderneath an aircraft, with the, ordnance shown in an ejected positionin phantom;

FIG. 2 is an exploded perspective view of the subject invention;

FIG. 3 is an exploded perspective view of the forward and rearwardactuator means of the subject invention and forward bell crank and therearward bell crank;

FIG. 4 is a side view of the forward and rearward actuator means, theenergy conduction means and the energy source of the subject invention;

FIG. 5 is an assembled perspective view of the subject invention;

FIG. 6 is a simplified side view of the hoist means of the subjectinvention shown with the rail disposed in a retracted position;

FIG. 7 is a simplified side view as in FIG. 6 showing the hoist means ofthe subject invention disengaged and the rail in an extended position;

FIG. 8 is a simplified side view as in FIGS. 6 and 7 showing the hoistmeans of the subject invention engaged so as to forcibly extend the railto an extended position; and

FIG. 9 is a perspective view of a portion of the hoist means of thesubject invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

Referring to the Figures, wherein like numerals are used to indicatelike or corresponding parts throughout the several views, an ordnanceejector apparatus according to the subject invention is generally shownat 10. In FIG. 1, the apparatus is shown disposed underneath a wing 12of an aircraft, generally indicated at 14. An ordnance 16 is shownsuspended under the apparatus 10. In order to safely deploy the ordnance16, the subject apparatus 10 extends downwardly from the aircraft wing12, as shown in phantom, to push the ordnance 16 through the turbulentboundary layer and into stable ambient air.

In FIGS. 2, 3 and 5, the apparatus 10 is shown including a support frame18 comprising right and left halves that respectively extending betweena forward end 20 and a rearward end 22 for fixed attachment to theaircraft 14. A rail, generally indicated at 24, extends between aforward end 26 and a rearward end 28 for releasably retaining anordnance 16 thereto. More specifically, the ordnance 16 is disposeddirectly below, and is suspended from, the rail 24. As shown in FIG. 2,the rail 24 includes a longitudinally extending vertical opening 30adjacent its forward end 26 for receiving a fin of the ordnance 16. Inthis manner, the ordnance is centrally supported under the rail 24 withits four outwardly extending forward stabilizer fins disposed in a "+"orientation. A spacer 32 is disposed within the forward end of theopening 30.

As shown in FIGS. 2 and 6-8, a forward link means, generally indicatedat 34, is pivotally connected between the forward end 20 of the supportframe 18 and the forward end 26 of the rail 24 for displacing theforward end 26 of the rail 24 a predetermined distance from the supportframe 18. The forward link means 34 includes a forward bell crank 36having pintles 38 pivotally received in sockets 40 adjacent the forwardends 20 of each of the support frames 18. The forward bell crank 36 hasa driving end 42 and a driven end 44. The forward link means 34 alsoincludes a forward connecting link 46 pivotally extending between thedriven end 44 of the forward bell crank 46 and the forward end 26 of therail 24. The forward bell crank 36 and forward connecting link 46generally resemble a half-scissor mechanism, as shown in the Figures.

A rearward link means, generally indicated at 48, is pivotally connectedbetween the rearward end 22 of each of the support frames 18 and therearward end 28 of the rail 24 for displacing the rearward end 28 of therail 24 a predetermined distance from the support frames 18. Therearward link means 48 includes a rearward bell crank 50 havingoutwardly extending pintles 52 pivotally received in correspondingsockets 54 adjacent the rearward ends 22 of the support frames 18. Therearward bell crank 50 has a driving end 56 and a driven end 58.

The rearward link means 48 further includes a rearward connecting link60 extending from a pivotal connection 62 at the rearward end 28 of therail 24 to a lost motion sliding connection, generally indicated at 64,at one of the support frames 18. The lost motion sliding connection 64includes a linear slot 66 disposed in one of the support frames 18 andextending generally longitudinally between the forward 20 and rearward22 ends of the one support frame 18. Therefore, the slot 66 is generallyhorizontal as shown in the Figures. A second slot, not shown in theFigures, is identical to and aligned with the slot 66 and disposed on abrace member 68 which is securely fastened between the two supportframes 18. The driven end 58 of the rearward bell crank 50 is pivotallyconnected to the rearward connecting link 60 generally midway betweenits pivotal connection 62 and its lost motion sliding connection 64. Therearward bell crank 50 and rearward connecting link 60 generallyresemble a three-quarter scissor mechanism, as shown in the Figures.

The apparatus 10 also includes a single energy source comprising a pairof replaceable cartridges each disposed in a cartridge holder 70. Thecartridges and their cartridge holders 70 are supported in a breechhousing 72. Preferably, the cartridges comprise a solid fuel, e.g.,nitroglycerin, pyrotechnic device for quickly generating largequantities of energy. The cartridge holders 70 are threadably receivingin the breech housing 72, and include tool engaging ends 74 to effect asecure seat within the breach housing 72.

As shown in FIGS. 2-4, the apparatus 10 includes a forward actuatormeans, generally indicated at 76, extending from the forward end of thebreech housing 72. The forward actuator means 76 is energized from thecartridges and operatively connected to the forward link means 34. Asshown in FIGS. 2 and 3, the forward actuator means 76 is connected tothe drive end 42 of the forward link means 34 for independentlycontrolling pivotal movement of the forward link means 34.

Referring again to FIG. 4, the forward actuator means 76 includes apiston 78 extending from a forward cylinder in the breech housing 72.The piston 78 generally comprises an elongated shaft having a distal end80 connected to the driving end 42 of the forward bell crank 36. Theforward piston 78 is surrounded by an outer jacket 82 which is fixed tothe breech housing 72. An annular flange 84 is disposed about theforward piston 78, within the jacket 82. Although not shown, acompression spring is disposed within the jacket 82, about the exteriorof the forward piston 78, and acts between the flange 84 and the insideend of the jacket 82 adjacent the distal end 80 of the forward piston78. Therefore, whenever the piston 78 is extended outwardly from thebreech housing 72, the compression spring is compressed within thejacket 82.

Similarly, a rearward actuator means, generally indicated 86, extendsfrom the breech housing 72. The rearward actuator means 86 is alsoenergized from the one common energy source, i.e., the cartridges, forindependently controlling the pivotal movement of the rearward linkmeans 48. As with the forward actuator means 76, the rearward actuatormeans 86 includes a rearward piston 88 extending from a cylinder in thebreech housing 72. The rearward piston 88 includes a distal end 90connected to the driving end 56 of the rearward bell crank 50. A flange92 is disposed annularly around the rearward piston 88, adjacent thebreech housing 72. A jacket 94 is fixedly connected to the breechhousing 72 and surrounds the piston 88. A compression spring, not shown,is disposed within the jacket 94 and bears against the flange 92 of therearward piston 88.

The breech housing 72, therefore, forms an interface between the forward76 and rearward 86 actuator means, as well as the energy sourcecartridges. The breech housing 72 supports the pistons 78, 88 such thatthey stroke in linearly opposite directions from one another. Moreimportantly, the breech housing 72 maintains the forward actuator means76 and rearward actuator means 86 such that they are fixedly aligned inaxially oppositely extending directions so that the linear output strokeof the forward piston 78 acts along a colinear and opposite directionfrom the linear output stroke of the rearward piston 88 to reduce thereaction forces between the forward and rearward actuator means 76, 86.

The breech housing 72 includes two outwardly extending support pins 96.As best shown in FIG. 3, the support pins 96 are disposed in respectivevertical sliders 98, which in turn are disposed within vertical tracks100. One of the vertical tracks is provided in the brace member 68 andthe other in one of the support frames 18. In this manner, as theforward 78 and rearward 88 pistons are stroked in order to rotate therespective bell cranks 36, 50, the entire breech housing 72 and attachedelements are permitted to rotate about the support pins 96 andvertically shift within the vertical tracks 100.

Referring again to FIG. 4, the subject apparatus 10 includes an energyconduction means, generally indicated at 102, for conducting energy fromthe energy source of the cartridges firstly to the forward actuatormeans 76 and secondly to the rearward actuator means 86 to initiatemovement of the forward link means 34 before movement of the rearwardlink means 48 to initially displace the rail 24 in a forward end 26 downcondition whereby the ordnance 16 is initially ejected in a forward end,or nose end, down condition. The energy conduction means 102 is disposedwithin the breech housing 72 and includes a velocity orifice 104 and apitch orifice 106. The internal routing and conduction lines disposedwithin the breech housing 72 extend from both of the cartridges in thecartridge holders 70 to the velocity orifice 104.

The velocity orifice 104 comprises a flow restriction which can be madeeither adjustable, or in the alternative non-adjustable. Ifnon-adjustable, the velocity orifice 104 would be replaceable withdifferent velocity orifices having different flow restrictioncharacteristics. The greater the flow restriction of the velocityorifice 104, the less energy is allowed to flow from the cartridges tothe forward 76 and rearward 86 actuator means. Therefore, the greaterthe flow restriction of the velocity orifice 104, the slower theresponse of the pistons 78, 88 and the slower the ordnance 16 will beejected.

The internal flow passages in the breech housing 72 extend from thevelocity orifice 104 directly to the cylinder inside the breech housing72 in which is disposed the forward piston 78. Therefore, energy, orgases, from the cartridges in the cartridge holders 70 pass firstthrough the velocity orifice 104 and then directly to the forward piston78, causing the forward link means 34 to begin moving. The energy isthen directed from the forward piston 78 to a pitch orifice 106.

The pitch orifice 106, like the velocity orifice 104, comprises a flowrestriction which can be made either adjustable or non-adjustable butreplaceable with different orifices having different flow restrictioncharacteristics. Energy flowing through the pitch orifice 106 isdirected to the cylinder in the breech housing 72 in which is disposedthe rearward piston 88. Therefore, by increasing the flow restriction ofthe pitch orifice 106, less energy will be directed to the rearwardpiston 88, thereby causing it to stroke more slowly. In this manner, thepitch of the rail 24, and hence the pitch of the ordnance 16 uponrelease, can be easily adjusted by changing the flow restriction of thepitch orifice 106.

Referring now to FIGS. 6-8, the subject invention includes a hoistmeans, generally indicated at 108, which operatively extends between thesupport frame 18 and the rail 24. As shown in the Figures, the hoistmeans 108 is mechanically connected between the support frame 18 and therail 24 for manually forcibly separating the rail 24 from the supportframe 18 in order to attach an ordnance 16 to the rail 24. That is, thehoist means 108 functions to force apart the rail 24 to an extendedposition as shown in FIG. 8 for the purpose of mounting an ordnance 16to the underside of the rail 24. Also, the hoist means 108 automaticallydisengages from the forward 76 and rearward 86 actuator means when theactuator means 76, 86 is actuated so as to allow uninterrupted ejectionof the ordnance 16, as illustrated in FIG. 7. That is, because the hoistmeans 108 remains continually operatively and connected between thesupport frame 18 and the rail 24, it must automatically disengage fromthe actuator means 76, 86 upon actuation so as not to interfere with theextension of the rail 24 upon ejection of the ordnance 16.

The hoist means 108 includes an elongated screw shaft 110 supported onthe support frame 18 for independent rotation. A travelling nut 112 isthreadably disposed on the screw shaft 110 for axial movement along thescrew shaft 110 in response to rotation thereof. As perhaps best shownin FIG. 2, the travelling nut 112 includes a pair of outwardly extendingpintles 114.

The hoist means 108 also includes a lever 116 extending between a firstend 118 having a pair of spaced openings 120 for pivotally receiving thepintles 114 of the travelling nut 112. The lever 116 also has a secondend 122 spaced from the first end 118, with a central fulcrum 124disposed approximately midway between first 118 and second 122 ends, asshown in FIG. 9. The second end 122 of the lever 116 includes a loadbearing surface 126 and a latch 128 spaced below the load bearingsurface 126. The latch 128 is pivotally disposed on the second end 122of the lever 116 and includes a coaxially spaced offset side cam 130moveable with the latch 128. Therefore, movement of the side cam 130causes a corresponding movement response in the latch 128.

The hoist means 108 further includes a brace 132 extending between alower end 134 and an upper end 136. The lower end 134 is pivotallyconnected to the support frame 118 along an axis A passing coaxiallythrough the central fulcrum 124 of the lever 116. Therefore, the hoistmeans 108 is pivotally attached to the support frame 118 about an axis Acommon to the pivotal attachment of the brace 132 to the support frame18. The brace 132 includes a member disposed adjacent the second end 122of the lever 116 and having a load bearing surface engaging portion 138,shown in FIGS. 6-8, and a latch engaging portion 140. As shown in FIG.9, the latch engaging portion 140 comprises a cylindrical rollerdisposed to engage the latch 128 of the lever 116.

Referring back to FIGS. 2-4, the breech housing 72 is shown including alinearly stroking firing piston 142 which is disposed upstream of theenergy source of the cartridges in the cartridge holders 70 from theforward actuator means 76. That is, the energy conduction means 102conducts energy from the fired cartridges first to the firing piston142, and then to the forward actuator means 76. In this manner, thefiring piston 142 is actuated chronologically first. In FIG. 4, thefiring piston 142 is shown in a stroked, or an actuated, position inphantom.

The brace 132 includes a pivotally supported trip finger 144 disposedadjacent the firing piston 142. An elongated shaft (not shown) extendsthrough the brace member, parallel to the axis A, to integrally connectthe trip finger 144 to a latch actuator 146. The latch actuator 146 isdisposed to engage the side cam 130 of the lever 116 when the latchengaging portion 140 of the brace 132 abuts the latch 128 of the lever116. Therefore, when the cartridges 170 are fired, the energy conductionmeans 102 conducts the energy first to the firing piston 142, whichstrokes linearly outwardly to engage and pivotally displace the tripfinger 144. Arcuate movement of the trip finger 144 causes the latchactuator 146 to rotate, thereby camming the side cam 130 pivotally aboutits integral support with the latch 128. The latch 128, thus, rotatesinwardly toward the lever 116, out from beneath the latch engagingportion 140. This allows the entire brace 132 to rotate about thefulcrum axis A free from the lever 116. As shown in FIG. 7, suchdisengagement of the brace 132 from the lever 116 disconnects the entirehoist means 108 from the actuator means 76, 86.

The hoist means 108 further includes a pair of push rods 148 operativelydisposed between the upper end 136 of the brace 132 and the rail 24. Asshown best in FIGS. 6-8, the operative connection of the push rods 148to the rail 24 are disposed generally midway between the forward 26 andrearward 28 ends of the rail 24. The push rods 148 serve two distinctfunctions.

The first function is for manually forcing the rail 24 to an extended,or semi-extended position, as shown in FIG. 8, for allowing ground crewpersonnel to attach an ordnance 16 to the rail 24. This is accomplishedby a ground crew member manually rotating the screw shaft 110 so as todisplace the travelling nut 112 axially upwardly along the screw shaft110. This movement of the travelling nut 112 causes the lever 116 torotate in a counterclockwise direction about the axis A, as viewed inFIGS. 6-8. Such rotation of the lever 116 causes the load bearingsurface 126 of the lever 116 to engage and forcibly displace the loadbearing engaging portion 138 of the brace 132, thereby causing the brace132 to rotate with the lever 116 counterclockwise about the fulcrum axisA. Such movement of the brace 132 causes an arcuate displacement of theupper end 136 of the brace 132. As the push rods 148 are pivotallyconnected between the upper ends 136 of the brace 132 and the rail 24,the rail 24 is displaced downwardly to an extended position, as shown inFIG. 8. This manual extension of the rail 24 also causes correspondingmovement of the forward link means 34 and the rearward link means 48.This, in turn, causes the forward actuator means 76 and rearwardactuator means 86 toward an extended position. The compression springsdisposed within the jackets 82, 94 of the respective actuator means 76,86 become depressed upon this manual extension of the rail 24, and laterassist in the retraction of the rail 24 when the travelling nut 112 ismanually moved back down the elongated screw shaft 110.

The second function of the push rods 148 is to form a safety latch tomaintain the rail 24 in a retracted position, as shown in FIG. 6, whenan ordnance 16 is attached to the aircraft 14. More specifically, thebrace 132 maintains the rail 24 in its retracted position by way of thelatch engaging portion 140 being immovably supported upon the latch 128of the lever 116. The lever 116, in turn, is restrained from rotationabout the fulcrum axis A by the connected travelling nut 112 andassociated screw shaft 110. Therefore, the rail 24 can not be extendedfrom the support frame 18 except by actuation of the cartridges wherebythe firing piston 142 is fired and extended from the breech housing 72to disengage the latch 128 from beneath the latch engaging portion 140.

Referring again to FIGS. 6-8, the rail 24 is shown including anautomatic ordnance release means, generally indicated at 150. Theautomatic ordnance release means 150 automatically releases the ordnance16 from its connection underneath the rail 24 in response to the rail 24reaching a predetermined spacing from the support frame 18. That is,when the rail 24 is extended from the support frame a preestablisheddistance, either by manual extension via the hoist means 108 orautomatic extension via the actuator means 76, 86, the ordnance 16 willbe automatically released from its connection to the rail 24.

This is accomplished by the automatic ordnance release means 150including a plurality of ordnance retaining hooks 152 moveably disposedon a rail 24. A cam 154 is fixedly disposed on the end of an elongatedshaft 156. The shaft 156 extends longitudinally along the rail 24 and isrotatably supported thereon, with the cam 154 being disposed adjacentthe forward end 26 of the rail 24. The elongated shaft 156 includesrelease actuators 158 operatively associated with each ordnanceretaining hooks 152.

The forward connecting link 46 includes an outwardly extending tooth 160disposed adjacent its pivotal connection to the forward end 26 of therail 24. The tooth 160 is disposed for operatively engaging the cam 154of the ordnance release means 150 in response to movement of the rail 24to a predetermined spacing from the support frame 18. Therefore, as therail 24 moves toward an extended position away from the support frame18, the forward connecting link 46 pivots in a clockwise direction aboutits pivotal connection to the forward end 26 of the rail 24, as viewedin FIGS. 6-8, so as to move the tooth 160 into engagement with the cam154, thereby rotating the cam 154 and connected shaft 156 within itssupport on the rail 24.

In the preferred embodiment, only two ordnance retaining hooks 152 areemployed on only one side of the rail 24, as shown best in FIG. 2. Aswill be appreciated, a plurality of sway braces 162 must be employed inassociation with the ordnance retaining hooks 152 in order to securelysupport the ordnance 116 during flight of the aircraft 14. The swaybraces 162 are fixedly attached to the support frame 18, as shown inFIG. 2. These sway braces 162 function only to support the ordnance whenthe rail 24 is in the fully retracted position. Once the rail 24 beginsmoving toward an extended position, the ordnance 16 is moved away fromthe sway braces 162 and is ejected from the rail 24 by the automaticordnance release means 150 when the rail 24 reaches a predeterminedspacing from the support frame 18.

OPERATION

A wiring harness 164 electrically connects the aircraft 14 guidancesystem and the aircraft 14 pilot to the ordnance ejector apparatus 10.Contained within the lever 116 is a switch (not shown) which allows theordnance 16 to be ejected when closed, and prevents the ordnance frombeing ejected when open. This switch can be closed electrically by thepilot, or manually by a member of the ground crew prior to take off.Prior to ejecting the ordnance 16, the pilot utilizes the aircraftguidance system to lock onto a target to which the ordnance 16 will bedirected.

When the pilot of the aircraft 14 electronically signals for theordnance to be ejected, an electrical signal is sent through the wiringharness 164 to the switch disposed in the lever 116, which travelsthrough the closed switch back through the wiring harness 164 to thebreech housing 72 at an electrical connection 166. The electrical signalentering the electrical connection 166 causes the pyrotechnic cartridgesdisposed within the cartridge holders 70 to simultaneously fire, causingenergy to be moved through the energy conduction means 102 first to thefiring piston 142 and then to the forward 76 and rearward 86 actuatormeans.

As the firing piston 142 is stroked outwardly, it engages and rotatesthe trip finger 144 on the brace 132, thereby causing the latch actuator146 to rotate against the side cam 130, ultimately disengaging the latch128 from the latch engaging portion 140 of the lever 116. Subsequently,the forward actuator means 76 begins moving the forward link means 34 todisplace the forward end 26 of the rail 24. Then, a fraction of a momentlater, the rearward actuator means 86 begins moving the rearward linkmeans 48 to displace downwardly the rearward end 28 of the rail 24. Asthe rail 24 is displaced downwardly toward and ejected condition, thetooth 160 on the forward connecting link 46 engages and rotates the cam154 of the automatic ordnance release means 150. When the cam 154 isfully actuated, the ordnance retaining hooks 152 fully disengage theordnance 16 from the rail 24 to effect complete separation of theordnance 16 from the apparatus 10.

Compression springs disposed within the jackets 82, 94 of the forward 76and rearward 86 actuator means, respectively, retract the forward 34 andrearward 48 link means back to a fully retracted position. As the rail24 moves back to the fully retracted position, the rods 148 of the brace132 rotate the brace 132 back to a position as shown in FIG. 6 wherebythe latch engaging portion 140 becomes automatically reengaged over thelatch 128.

The invention has been described in an illustrative manner, and it is tobe understood that the terminology which has been used is intended to bein the nature of words of description rather than of limitation.

Obviously, many modifications and variations of the present inventionare possible in light of the above teachings. It is, therefore, to beunderstood that within the scope of the appended claims whereinreference numerals are merely for convenience and are not to be in anyway limiting, the invention may be practiced otherwise than asspecifically described.

What is claimed is:
 1. An ordnance ejector apparatus (10) for ejectingan ordnance (16) for an aircraft (14) comprising: a support frame (18)extending between a forward end (20) and a rearward end (22) for fixedattachment to an aircraft (14); a rail (24) extending between a forwardend (26) and a rearward end (28) for releaseably retaining an ordnance(16) thereto; forward link means (34) pivotally connected to saidforward end (20) of said support frame (18) and said forward end (26) ofsaid rail (24) for displacing said forward end (26) of said rail (24)from said forward end (20) of said support frame (18) a predetermineddistance; rearward link means (48) pivotally connecting said rearwardend (22) of said support frame (18) and said rearward end (28) of saidrail (24) for displacing said rearward end (28) of said rail (24) fromsaid rearward end (22) of said support frame (18) a predetermineddistance; forward actuator means (76) having an output stroke along alinear path for controlling the pivotal movement of said forward linkmeans (34); rearward actuator means (86) having an output stroke along alinear path for controlling the pivotal movement of said rearward linkmeans (48); and characterized by said forward actuator means (76) andsaid rearward actuator means (86) being fixedly aligned in an axiallyoppositely extending disposition such that the linear output stroke ofsaid forward actuator means (76) acts along a colinear and oppositedirection from the linear output stroke of said rearward actuator means(86) to reduce reaction forces between said forward (76) and rearward(86) actuator means.
 2. An apparatus (10) as set forth in claim 1further characterized including a breech housing (72) moveably supportedon said support frame (18) and integrally connecting said forward (76)and rearward (86) actuator means.
 3. An apparatus (10) as set forth inclaim 2 further characterized by including a single energy source forenergizing each of said forward (76) and rearward (86) actuator means.4. An apparatus (10) as set forth in claim 3 further characterized bysaid energy source being disposed in a cartridge holder (70) fixedlyattached to said breech housing (72).
 5. An apparatus (10) as set forthin claim 4 further characterized by including vertical sliders (98)slideably disposed in corresponding vertical tracks (100) in saidsupport frame (18) for pivotally and slideably mounting said breechhousing (72) to said support frame (18).
 6. An apparatus (10) as setforth in claim 4 further characterized by said breech housing (72)including a linearly stroking firing piston (142) disposed upstream ofsaid energy source from said forward actuator means (76).
 7. Anapparatus (10) as set forth in claim 6 further characterized by saidenergy source including as least one pyrotechnically operatedreplaceable cartridge.
 8. An apparatus (10) as set forth in claim 7further characterized by said forward link means (34) including aforward bell crank (36) pivotally disposed in said forward end (20) ofsaid support frame (18) and having a driving end (42) in a driven end(44).
 9. An apparatus (10) as set forth in claim 8 further characterizedby said forward actuator means (86) comprising a linearly reciprocatingforward piston (78) having a distal end (80) pivotally connected to saiddriving end (42) of said forward bell crank (46).
 10. An apparatus (10)as set forth in claim 9 further characterized by said rearward linkmeans (48) including a rearward bell crank (50) pivotally disposed insaid rearward end (22) of said support frame (18) and having a drivingend (56) and a driven end (58).
 11. An apparatus (10) as set forth inclaim 10 further characterized by said rearward actuator means (86)comprising a linearly reciprocating rearward piston (88) having a distalend (90) pivotally connected to said driving end (56) of said rearwardbell crank (50).
 12. An apparatus (10) as set forth in claim 11 furthercharacterized by said forward link means (34) including a forwardconnecting link (46) pivotally extending between said driven end (44) ofsaid forward bell crank (36) and said forward end (26) of said rail(24).
 13. An apparatus (10) as set forth in claim 12 furthercharacterized by said rearward link means (48) including a rearwardconnecting link (60) extending from a pivotal connection (62) at saidrearward end (28) of said rail (24) to a lost motion sliding connection(64) at said support frame (18).
 14. An apparatus (10) as set forth inclaim 13 further characterized by said driven end (58) of said rearwardbell crank (50) being pivotally connected to said rearward connectinglink (60) generally midway between said pivotal connection (62) and saidlost motion sliding connection (64).
 15. An apparatus (10) as set forthin claim 14 further characterized by said lost motion sliding connection(64) including a linear slot (66) disposed in said support frame (18)and extending generally longitudinally between said forward (20) andsaid rearward (22) ends of said support frame (18).